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Docket No. FAA-2004-18379,72 FR 63409, Nov. 8, 2007, unless otherwise noted.
Docket No. FAA-2005-22997,73 FR 42499, July 21, 2008, unless otherwise noted.
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(a)Applicability. This section applies to U.S. type certificated transport category, turbine-powered airplanes, other than those designed solely for all-cargo operations, for which the State of Manufacture issued the original certificate of airworthiness or export airworthiness approval on or after January 1, 1992, that, as a result of original type certification or later increase in capacity have:
(1) A maximum type-certificated passenger capacity of 30 or more, or
(2) A maximum payload capacity of 7,500 pounds or more.
(b)Flammability Exposure Analysis.
(1)General. Within 150 days after December 26, 2008, holders of type certificates must submit for approval to the responsible Aircraft Certification Service office a flammability exposure analysis of all fuel tanks defined in the type design, as well as all design variations approved under the type certificate that affect flammability exposure. This analysis must be conducted in accordance with Appendix N ofpart 25 of this chapter.
(2)Exception. Thisparagraph (b) does not apply to—
(i) Fuel tanks for which the type certificate holder has notified the FAA underparagraph (g) of this section that it will provide design changes and service instructions for Flammability Reduction Means or an Ignition Mitigation Means (IMM) meeting the requirements ofparagraph (c) of this section.
(ii) Fuel tanks substantiated to be conventional unheated aluminum wing tanks.
(c)Design Changes. For fuel tanks with a Fleet Average Flammability Exposure exceeding 7 percent, one of the following design changes must be made.
(1)Flammability Reduction Means (FRM). A means must be provided to reduce the fuel tank flammability.
(i) Fuel tanks that are designed to be Normally Emptied must meet the flammability exposure criteria of Appendix M ofpart 25 of this chapter if any portion of the tank is located within the fuselage contour.
(ii) For all other fuel tanks, the FRM must meet all of the requirements of Appendix M ofpart 25 of this chapter, except, instead of complying with paragraph M25.1 of this appendix, the Fleet Average Flammability Exposure may not exceed 7 percent.
(2)Ignition Mitigation Means (IMM). A means must be provided to mitigate the effects of an ignition of fuel vapors within the fuel tank such that no damage caused by an ignition will prevent continued safe flight and landing.
(d)Service Instructions. No later than December 27, 2010, holders of type certificates required byparagraph (c) of this section to make design changes must meet the requirements specified in eitherparagraph (d)(1) or(d)(2) of this section. The required service instructions must identify each airplane subject to the applicability provisions ofparagraph (a) of this section.
(1)FRM. The type certificate holder must submit for approval by the responsible Aircraft Certification Service office design changes and service instructions for installation of fuel tank flammability reduction means (FRM) meeting the criteria ofparagraph (c) of this section.
(2)IMM. The type certificate holder must submit for approval by the responsible Aircraft Certification Service office design changes and service instructions for installation of fuel tank IMM that comply with14 CFR 25.981(c) in effect on December 26, 2008.
(e)Instructions for Continued Airworthiness (ICA). No later than December 27, 2010, holders of type certificates required byparagraph (c) of this section to make design changes must submit for approval by the responsible Aircraft Certification Service office, critical design configuration control limitations (CDCCL), inspections, or other procedures to prevent increasing the flammability exposure of any tanks equipped with FRM above that permitted underparagraph (c)(1) of this section and to prevent degradation of the performance of any IMM provided underparagraph (c)(2) of this section. These CDCCL, inspections, and procedures must be included in the Airworthiness Limitations Section (ALS) of the ICA required by14 CFR 25.1529 orparagraph (f) of this section. Unless shown to be impracticable, visible means to identify critical features of the design must be placed in areas of the airplane where foreseeable maintenance actions, repairs, or alterations may compromise the critical design configuration limitations. These visible means must also be identified as a CDCCL.
(f)Airworthiness Limitations. Unless previously accomplished, no later than December 27, 2010, holders of type certificates affected by this section must establish an ALS of the maintenance manual or ICA for each airplane configuration evaluated underparagraph (b)(1) of this section and submit it to the responsible Aircraft Certification Service office for approval. The ALS must include a section that contains the CDCCL, inspections, or other procedures developed underparagraph (e) of this section.
(g)Compliance Plan for Flammability Exposure Analysis. Within 90 days after December 26, 2008, each holder of a type certificate required to comply withparagraph (b) of this section must submit to the responsible Aircraft Certification Service office a compliance plan consisting of the following:
(1) A proposed project schedule for submitting the required analysis, or a determination that compliance withparagraph (b) of this section is not required because design changes and service instructions for FRM or IMM will be developed and made available as required by this section.
(2) A proposed means of compliance withparagraph (b) of this section, if applicable.
(h)Compliance Plan for Design Changes and Service Instructions. Within 210 days after December 26, 2008, each holder of a type certificate required to comply withparagraph (d) of this section must submit to the responsible Aircraft Certification Service office a compliance plan consisting of the following:
(1) A proposed project schedule, identifying all major milestones, for meeting the compliance dates specified inparagraphs (d),(e) and(f) of this section.
(2) A proposed means of compliance withparagraphs (d),(e) and(f) of this section.
(3) A proposal for submitting a draft of all compliance items required byparagraphs (d),(e) and(f) of this section for review by the responsible Aircraft Certification Service office not less than 60 days before the compliance times specified in those paragraphs.
(4) A proposal for how the approved service information and any necessary modification parts will be made available to affected persons.
(i) Each affected type certificate holder must implement the compliance plans, or later revisions, as approved underparagraph (g) and(h) of this section.
[Doc. No. FAA-2005-22997,73 FR 42499, July 21, 2008, as amended by Amdt. 26-3,74 FR 31619, July 2, 2009; Doc. No. FAA-2018-0119, Amdt. 26-7,83 FR 9169, Mar. 5, 2018]